固体火箭冲压发动机补燃室燃烧过程显示

胡建新; 夏智勋; 张龙; 郭健; 张炜; 申慧君; 王德全; 黄利亚

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固体火箭冲压发动机补燃室燃烧过程显示
胡建新¹, 夏智勋², 张龙³, 郭健⁴, 张炜⁵, 申慧君⁶, 王德全⁷, 黄利亚⁸
1.国防科学技术大学航天与材料工程学院湖南长沙410073;2.国防科学技术大学航天与材料工程学院湖南长沙410074;3.国防科学技术大学航天与材料工程学院湖南长沙410075;4.国防科学技术大学航天与材料工程学院湖南长沙410076;5.国防科学技术大学航天与材料工程学院湖南长沙410077;6.国防科学技术大学航天与材料工程学院湖南长沙410078;7.国防科学技术大学航天与材料工程学院湖南长沙410079;8.国防科学技术大学航天与材料工程学院湖南长沙410080

摘要:

采用二维开窗式固体火箭冲压发动机试验系统,对补燃室内的燃烧现象进行观察,以火焰图像的形式直观形象地描述了进气道位置对补燃室内燃烧过程的影响,试验所采用的装药为含硼贫氧推进剂。并通过高速数字摄影仪摄取补燃室内部某个时刻瞬时火焰图像,借助于光学理论和计算机图像处理技术计算出整个补燃室内部的温度分布。

关键词: 固体火箭冲压发动机补燃室含硼推进剂燃烧试验温度测量图像处理

DOI：

分类号:V435

基金项目:国家自然科学基金(50376072)

Combustion process in secondary combustion chamber of ducted rocket by high speed photography and digital image processing

HU Jian-xin¹, XIA Zhi-xun², ZHANG long³, GUO Jian⁴, ZHANG Wei⁵, SHEN Hui-jun⁶, WANG De-quan⁷, HUANG Li-ya⁸

1.Inst.of Aerospace and material Engineering,National Univ.of Defense Technology,Changsha 410073,China;2.Inst.of Aerospace and material Engineering,National Univ.of Defense Technology,Changsha 410074,China;3.Inst.of Aerospace and material Engineering,National Univ.of Defense Technology,Changsha 410075,China;4.Inst.of Aerospace and material Engineering,National Univ.of Defense Technology,Changsha 410076,China;5.Inst.of Aerospace and material Engineering,National Univ.of Defense Technology,Changsha 410077,China;6.Inst.of Aerospace and material Engineering,National Univ.of Defense Technology,Changsha 410078,China;7.Inst.of Aerospace and material Engineering,National Univ.of Defense Technology,Changsha 410079,China;8.Inst.of Aerospace and material Engineering,National Univ.of Defense Technology,Changsha 410080,China

Abstract:

In order to get better insight in the combustion behavior of the secondary combustion chambers,a high-speed photography has been used to analyze the highly turbulent multiphase combustion flow.During the test,boron-based fuel-rich HTPB propellant is used.The portion of the primary plume is viewed through a quartz window and is recorded by photography.The geometry has been designed with a square section for the duct to facilitate optical access inside the combustor.Rebuild the combustion flame’s temperature field by applying the digital image processing technology.

Key words: Ducted rocket Secondary combustion chamber Boron-based propellant Combustion experiment Temperature measurement Digital image processing